CN104048323A

CN104048323A - System of multi-tube fuel nozzles with fuel nozzle housing

Info

Publication number: CN104048323A
Application number: CN201410093498.0A
Authority: CN
Inventors: J.T.斯图尔特; C.P.基纳; H.M.奥斯特比
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2013-03-15
Filing date: 2014-03-13
Publication date: 2014-09-17
Also published as: DE102014103085A1; JP2014181900A; JP6483957B2; US9303873B2; CH707843A2; US20140338344A1; CH707843A8

Abstract

The invention discloses a system. The system comprises a plurality of multi-tube fuel nozzles, wherin each multi-tube fuel nozzle is provided with a plurality of tubes extending in the axial direction, and each tube comprise an air inlet, a fuel inlet and a fuel-air mixture outlet; and a fuel nozzle housing, wherein the fuel nozzle housing comprises an outer wall surrounding the central axial line and extending in the circumferential direction, a plurality of radial walls extending from the outer wall towards the central axial line, a plurality of fuel nozzle containers arranged in the outer wall, and a mouting structure which includes a plurality of radial supporting arms extending outwards from the outer wall. The plurality of fuel nozzle containers are separated from each other by the plurality of radial walls, and the multi-tube fuel nozzles are arranged in the plurality of fuel nozzle containers.

Description

Comprise the system with the multitube fuel nozzle of fuel nozzle shell

Technical field

The disclosed theme of this description relates to a kind of gas-turbine unit, and more properly, relates to a kind of fuel nozzle of the burner for described gas-turbine unit.

Background technology

Gas-turbine unit generally includes the burner of turbine and carrying fuel nozzle.The mixture of fuel and air burns in burner, to produce hot burning gases, the turbo blade in the combustion gases drive turbine of heat rotates, and drives again the axle in the load that is connected to for example generator to rotate.Fuel air mixture (uniformity that for example, in burner, fuel-air mixes) can significantly affect power stage, efficiency and the exhaust emissions of gas-turbine unit.In addition, in burner fuel air mixture burning can cause burning dynamically, vibration and thermal gradient, they can affect as the performance of each combustor component of fuel nozzle and life-span.For example, fuel nozzle may because of its immediately heat combustion product through the growth of being heated.These burning correlation effects may make the design of gas-turbine unit, especially burner and fuel nozzle design become complicated.

Summary of the invention

Below summarize and original desired invention suitable some embodiment in scope.These embodiment are not intended to limit desired invention scope, and on the contrary, these embodiment are only intended to summarize possibility form of the present invention.Actual, the present invention can be contained various forms that may be similar or different from following embodiment.

In an embodiment, as the application's first aspect, a kind of system comprises multiple multitube fuel nozzles, and each multitube fuel nozzle has the multiple pipes that extend in the axial direction, and in wherein said multiple pipes, each pipe comprises air intake, fuel inlet and fuel air mixture outlet; And fuel nozzle shell, described fuel nozzle shell comprises: outer wall, and described outer wall circumferentially extends around central axis; Multiple radial walls, described multiple radial walls inwardly extend towards described central axis from described outer wall; Multiple fuel nozzle containers, described multiple fuel nozzle containers are arranged in described outer wall, and wherein said multiple radial walls are separated from each other described multiple fuel nozzle container, and described multiple multitube fuel nozzle is arranged in described multiple fuel nozzle container; Mounting structure, described mounting structure comprises from the outward extending multiple radial support arms of described outer wall.

Second aspect, as above the system described in embodiment, each fuel nozzle in wherein said multiple multitube fuel nozzle has the described multiple pipes that expose around respective fuel injector girth, and described fuel nozzle shell extends around the described girth of each fuel nozzle.

The third aspect, as above the system described in embodiment, wherein said multiple fuel nozzle container comprises the first container and second container, and described multiple multitube fuel nozzle comprises the first multitube fuel nozzle being arranged in described the first container and is arranged on the second multitube fuel nozzle in described second container.

Fourth aspect, the as above system described in the third aspect, wherein said multiple fuel nozzle containers comprise the 3rd container, and described multiple multitube fuel nozzle comprises the 3rd multitube fuel nozzle being arranged in described the 3rd container.

The 5th aspect, as above the system described in fourth aspect, wherein said the first container comprises the first cheese girth being limited at least partly by the first and second radial walls in described outer wall and described multiple radial wall, described second container comprises the second cheese girth being limited at least partly by second in described outer wall and described multiple radial wall and the 3rd radial wall, and described the 3rd container comprises the 3rd cheese girth being limited at least partly by first in described outer wall and described multiple radial wall and the 3rd radial wall.

The 6th aspect, the as above system described in the 5th aspect, wherein said outer wall comprises the ring-type outer wall around border circular areas, wherein said first, second and the 3rd cheese girth comprise separately and account for the fan-shaped of described border circular areas approximately 120 degree.

The 7th aspect, the as above system described in embodiment, wherein said fuel nozzle shell comprises the inwall coaxial with described outer wall cardinal principle, wherein said inwall is connected to described multiple radial wall.

Eight aspect, the as above system described in the 7th aspect, it comprises center fuel nozzle, described center fuel nozzle is arranged in the central passage that extends through described inwall.

The 9th aspect, the as above system described in embodiment, the each container in wherein said multiple fuel nozzle containers is connected to a fuel channel by least one arm in described multiple radial support arms.

The tenth aspect, the as above system described in embodiment, the each wall in wherein said multiple radial walls comprises at least one hole, between the adjacent container of described at least one hole in described multiple fuel nozzle containers, extends.

The tenth on the one hand, the as above system described in the tenth aspect, and at least one arm in wherein said multiple radial support arms comprises fuel channel, described fuel channel extends in described multiple container.

The 12 aspect, the as above system described in embodiment, the each arm in wherein said multiple radial support arms comprises airfoil cross section.

The tenth three aspects:, the as above system described in embodiment, wherein said mounting structure comprises the outward flange circumferentially extending around described outer wall, wherein said multiple radial support arms are radially extended between described outward flange and described outer wall.

The 14 aspect, as above the system described in the tenth three aspects:, it has comprised the fuel flange that is connected to described outward flange, wherein fuel channel extend through described fuel flange, by described outward flange, by an arm in described multiple radial support arms, by described outer wall, and enter in a container in described multiple fuel nozzle container.

The 15 aspect, the as above system described in embodiment, wherein said outer wall comprises: the first installation portion, described the first installation portion is configured for and supports inlet flow rate adjuster; And second installation portion, board component after described the second installation portion is configured for and supports, wherein said the first installation portion and described the second installation portion are axially offset to one another.

The 16 aspect, the as above system described in embodiment, wherein said the first installation portion and described the second installation portion comprise be separately arranged in described outer wall multiple radial openings, be connected to multiple radial peg of described outer wall or its combination.

The 17 aspect, the as above system described in embodiment, it has comprised burner, gas-turbine unit or its combination with described multiple multitube fuel nozzle and described fuel nozzle shell.

In another embodiment, as the application's the tenth eight aspect, a kind of system comprises fuel nozzle shell, and described fuel nozzle shell comprises: outer wall, and described outer wall circumferentially extends around central axis; Multiple radial walls, described multiple radial walls inwardly extend towards described central axis from described outer wall; Multiple fuel nozzle containers, described multiple fuel nozzle containers are arranged in described outer wall, and wherein said multiple radial walls are separated from each other described multiple fuel nozzle container, and described multiple fuel nozzle container is configured for the multiple multitube fuel nozzles of support; Mounting structure, described mounting structure comprises from the outward extending multiple radial support arms of described outer wall.

The 19 aspect, as above the system described in the tenth eight aspect, wherein said mounting structure comprises the outward flange circumferentially extending around described outer wall, described multiple radial support arms is radially extended between described outward flange and described outer wall, and at least one arm in described multiple radial support arms comprises the fuel channel of extending in described multiple container.

In another embodiment, a kind of method comprises: multiple multitube fuel nozzles are supported in fuel nozzle shell, and wherein said fuel nozzle shell comprises: outer wall, and described outer wall circumferentially extends around central axis; Multiple radial walls, described multiple radial walls inwardly extend towards described central axis from described outer wall; And multiple fuel nozzle containers, described multiple fuel nozzle container is arranged in described outer wall, wherein said multiple radial wall is separated from each other described multiple fuel nozzle container, and wherein said multiple multitube fuel nozzles are arranged in described multiple fuel nozzle container; And with mounting structure, described fuel nozzle shell is installed, described mounting structure has from the outward extending multiple radial support arms of described outer wall.

Brief description of the drawings

While detailed description in detail below reading with reference to accompanying drawing, will understand better these and other features of the present invention, aspect and advantage, in the accompanying drawings, similarity sign represents similar part, wherein:

Fig. 1 is according to the block diagram of the turbine system with micro-mixer system of embodiment;

Fig. 2 is according to the cross section perspective side elevation view of the burner with the system of micro-mixer shown in Fig. 1 of embodiment;

Fig. 3 is according to the side view of the micro-mixer system of embodiment;

Fig. 4 is according to the decomposition perspective cross-sectional view of the micro-mixer system of embodiment;

Fig. 5 is according to the decomposition diagram of the fuel nozzle shell of embodiment and multitube fuel nozzle;

Fig. 6 is according to the front view of the fuel nozzle shell of embodiment;

Fig. 7 is according to the front view of the fuel nozzle shell of embodiment;

Fig. 8 is according to the front view of the fuel nozzle shell of embodiment;

Fig. 9 is according to the partial cross section view of the micro-mixer system of embodiment;

Figure 10 is the sectional view of the system of micro-mixer shown in Fig. 9 10-10 along the line, and the embodiment of elastic metallic seal is shown;

Figure 11 is the front end view with the elastic metallic seal embodiment of the fan-shaped configuration that is suitable for the fan-shaped fuel nozzle of Figure 4 and 5;

Figure 12 is the sectional view of the 10-10 along the line of fuel nozzle shown in Fig. 9, and the embodiment of the elastic metallic seal that has single turning or turn round is shown;

Figure 13 is the sectional view of the 10-10 along the line of fuel nozzle shown in Fig. 9, and the embodiment of the elastic metallic seal that has multiple turnings or turn round is shown;

Figure 14 is the sectional view of the 10-10 along the line of fuel nozzle shown in Fig. 9, thereby the embodiment that has multiple turnings or turn round the elastic metallic seal that limits bellows is shown;

Figure 15 is according to the decomposition diagram of the rear board component of embodiment;

Figure 16 is according to the sectional view of micro-mixer system 16-16 along the line in Fig. 9 of embodiment;

Figure 17 is according to the sectional view of the rear plate of embodiment;

Figure 18 is according to the rear view of the inlet flow rate adjuster of the fuel nozzle of embodiment;

Figure 19 is according to the front perspective view of the inlet flow rate adjuster of embodiment;

Figure 20 is according to the partial cross section view of the inlet flow rate adjuster of embodiment;

Figure 21 is according to the partial cross section view of the inlet flow rate adjuster of embodiment; And

Figure 22 is according to the partial cross section view of the inlet flow rate adjuster of embodiment.

Detailed description of the invention

Below will be described one or more specific embodiment of the present invention.For the concise and to the point description for these embodiment is provided, all features in actual implementation may not can be described in this manual.Should understand, develop any this type of actual implementation in any engineering or design object time, must make the various decision-makings with implementation certain relevant, to realize developer's intended target, as observed, system is relevant retrains with traffic aided, and these constraints may be different different because of implementation.In addition, should understand, this type of development may be complicated and consuming time, but for benefiting from those skilled in the art of the present invention in affiliated field, this is by the normal work to do in being still design, manufacturing and producing.

In the time of the element of introducing in various embodiments of the present invention, article " ", " one ", " being somebody's turn to do " and " described " are intended to indicate one or more this elements.Term " comprises ", " comprising " and " having " be intended to represent comprising property implication and represent except listed element, may also have other element.

Various embodiments of the present invention provide a kind of micro-mixer system, described micro-mixer system (for example comprises entrance flow regulator, rear board component, multitube fuel nozzle, cylindrical or fan-shaped fuel nozzle), elastic metallic seal (for example, metal bellows) and fuel nozzle shell.In some embodiment, multitube fuel nozzle can comprise 5 to 1000,10 to 500,20 to 250 or 30 to 100 mixing tubes, and they for example, are essentially parallel to each other in one or more groups (, 1,2,3,4,5,6 or more groups).Each mixing tube can be approximately 0.25 to 5 centimetres, 0.5 to 3 centimetre or 1 to 2 centimetre on diameter.Multiple mixing tubes in multitube fuel nozzle make fuel and air can mix on a small scale (for example, micro-mixing), thereby help to improve the uniformity that in burner, fuel-air mixes.

Fuel nozzle shell is by being connected to inlet flow rate adjuster and rear board component and supporting micro-mixer system by receiving multitube fuel nozzle.In the time of assembling, inlet flow rate adjuster covers multitube fuel nozzle with rear board component by the relative end that is connected to fuel nozzle shell.In some embodiment, fuel nozzle shell can comprise the first ring structure (, interior ring structure) and the second ring structure (, outer ring structure) that link together by pole.Fuel nozzle shell can be received in multitube fuel nozzle in interior ring structure and by fuel radial delivery to multitube fuel nozzle.Exactly, fuel nozzle shell configurable for substantially in the radial direction transfer the fuel by outer ring structure, interior ring structure and by interior ring structure being connected to the pole of outer ring structure.Fuel radial delivery can comprise combustion gas turbine systems to be positioned at the simple end plate (for example, carry hole or do not have fuel to carry the end plate of hole with minimum fuel) of burner end.Radial fuel is carried also can increase the usage space of fuel nozzle in burner (, the pipe of multitube fuel nozzle can occupy previously carry out fuel by end plate carry space used).

Pole in fuel nozzle shell can comprise that fuel carries pole and/or on-fuel carries pole.Fuel nozzle shell pole makes it possible to carry out radial fuel conveying, and can increase vibration (for example, micro-mixer system resonance) resistance.For example, pole can increase fuel nozzle shell rigidity and/or change micro-mixer system resonance frequency.In addition, pole can be shaped according to aerodynamics (for example, wing shapes), to reduce by the compressed air wake flow between outer ring structure and interior ring structure.Wake flow reduces and also can reduce in micro-mixer system by the vibration causing by the compressed air stream of burner.

Finally, fuel nozzle shell allows to realize modular micro-mixer system.For example, fuel nozzle shell can comprise multiple radially holes, and described multiple radially holes make the parts of micro-mixer system can be easily attached and separate.Exactly, hole can receive pin or other securing member, so that inlet flow rate adjuster and rear board component are connected to fuel nozzle shell.The simple attached of inlet flow rate adjuster and rear board component made it possible to easily approach, safeguards or changes multitube fuel nozzle, inlet flow rate adjuster, rear board component and elastic metallic seal with separating.

In operation, micro-mixer system is mixed air and fuel in multitube fuel nozzle, to form fuel air mixture.Fuel air mixture burns in burner, to form the burning gases that drive turbine.Multitube fuel nozzle can comprise with the first plate of first group of opening, with the second plate of second group of opening with extend through multiple pipes of the opening group in the first and second plates.In described pipe, each pipe can have at the air intake at the first axial end place, fuel inlet between first and second axial end and be positioned at the fuel air mixture outlet at the second axial end place.Specifically; following discussion, each pipe is configured for fuel and the air in premix (for example,, to mix on a small scale micro-mixing in other words) respective tube; and for example export subsequently fuel air mixture, for burning in burner (, the turbine burner of gas-turbine unit).The air themperature that enters multitube fuel nozzle can raise to air acting a little because of compression, for example, approximately 200 to 500 degrees Celsius, can be significantly colder and enter the fuel of pipe, for example, approximately 20 to 250 degrees Celsius.In addition, because pipe is close to combustion reaction, therefore can be easy to be heated by hot combustion product.Therefore, in operation (for example, in combustion chamber, burn) in, each parts of multitube fuel nozzle, shell mechanism, burner, fuel feed line, installation portion etc. may stand the thermal expansion of different rates, thereby cause faster swelling part to apply power to slower swelling part.For example, the thermal expansion rates that the multiple pipes in multitube fuel nozzle stand may be larger than the thermal expansion rates of around fuel sheath structure, installation portion, burner and/or other structures.

In order to slow down the induced stress being caused by thermal expansion and/or the contraction of component materials, micro-mixer system can comprise elastic metallic seal (for example, metal bellows).For example, metal bellows around the wall of the spatial placement that comprises plate and pipe assembly (for example can have, ring-type or acyclic wall), wherein said wall has one or more turnings or (for example turns round, waveform, vibration or zigzag pattern), they can elastic foldable or the wall energy launched to make metal bellows expand and shrink.Therefore, elasticity adjustable (for example, the folding and expansion of wall) makes metal bellows can adapt to plate, pipe assembly and the thermal expansion between parts and contraction around.For example do not having, in the situation of elastic metallic seal (, metal bellows), axial displacement can cause stress, fuel/air mixture leakage, burner internal pressure loss or other negative effects in multitube fuel nozzle parts.In the time being placed between the first plate and shell mechanism, elastic metallic seal (for example, metal bellows) thus can expand in the axial direction or shrink the thermal expansion or the blockage effect that reduce pipe, maintain between the chamber in fuel nozzle continuous operation sealing simultaneously.In addition, the use of elastic metallic seal can make to design more modularization, and therefore, structure is easy, assembling/unloading process is simple, equipment replacement cost, and safeguards that reduce downtime.

Micro-mixer system also can comprise rear board component, to the other protection to multitube fuel nozzle (, opposing thermal stress) is provided.Exactly, rear board component can stop direct contact the between combustion reaction and multitube fuel nozzle in burner, also can be formed for the air cooling chamber of the cooling multitube fuel nozzle of convection current.Although the cooling multitube fuel nozzle of air cooling chamber convection current, directly contacts between rear board component prevention combustion reaction and multitube fuel nozzle.Exactly, rear board component comprises rear plate, and described rear strip has the fuel air mixture of permission to leave the hole of multitube fuel nozzle, and covers the heat transfer from combustion reaction with opposing of multitube fuel nozzle simultaneously.In some embodiment, rear plate can comprise thermal barrier coating, to increase the thermal resistance to combustion reaction.In further embodiments, rear plate can comprise the cooling hole of diffusion that receives air-flow from air cooling chamber.Spread cooling hole and on rear plate, form cooling film, after described cooling film protection, plate and minimizing are conducted heat.In other embodiment, rear board component can comprise and being configured for before cooling blast leaves the cooling hole of diffusion gas shock to the shock plate on rear plate, increases thus the heat transfer of the heat of rear plate being protected and reduced to multitube fuel nozzle.In operation, shock plate makes cooling blast flow through impact opening with it to accelerate.Impact opening guides cooling blast to contact with rear plate, and wherein cooling blast is passing the front absorption heat of rear plate (for example, the space through the cooling hole of diffusion and/or rear plate and the pipe of multitube fuel nozzle).

Finally, micro-mixer system can comprise entrance flow regulator.Inlet flow rate regulator configuration is used for filtering the air-flow that enters micro-mixer system, and air-flow is evenly distributed in each pipe of multitube fuel nozzle.For airflow filtering is arrived among micro-mixer system, inlet flow rate adjuster can comprise the hole less than the hole in the pipe of multitube fuel nozzle.The fragment that therefore, can enter in the pipe of multitube fuel nozzle can be stoped by inlet flow rate adjuster.As mentioned above, inlet flow rate adjuster can be evenly distributed to air-flow in each pipe of multitube fuel nozzle.Exactly, inlet flow rate adjuster can comprise radially hole and turn to guiding element, and air-flow is directed to the outermost tubes in multitube fuel nozzle by they.But, in other embodiment, inlet flow rate adjuster can comprise combined or not combination have the hole of the inclination that turns to guiding element, to air-flow is directed to the outermost tubes in multitube fuel nozzle.By air-flow being evenly distributed to the pipe of multitube fuel nozzle, multitube fuel nozzle mixes and distribution fuel air mixture with suitable ratio, to realize best combustion, discharge, fuel consumption and power stage.Exactly, micro-mixer system can reduce unexpected emission (for example, the NO from combustion gas turbine systems _x, CO, CO ₂etc.) level.

Fig. 1 is the block diagram of combustion gas turbine systems 10.Discussed in more detail below, disclosed turbine system 10 can adopt the fuel nozzle (for example, multitube fuel nozzle) of one or more radial support.Turbine system 10 can use liquid or gaseous fuel (as natural gas and/or hydrogen-rich synthetic gas) to drive turbine system 10.As depicted, burner 12 is from 14 air inlets of fuel supply source, fuel mixed with air in the interior distribution of burner 12 burning.Exactly, burner 12 comprises micro-mixer system 16, described micro-mixer system 16 radial support multitube fuel nozzles and provide fuel to it.In some embodiment, micro-mixer system 16 comprises multiple fuel nozzles of arranging around center fuel nozzle.Multitube fuel nozzle mixes and distribution fuel air mixture with suitable ratio, to realize best combustion, discharge, fuel consumption and power stage.Exactly, micro-mixer system 16 has reduced unexpected emission (for example, the NO from turbine system 10 _x, CO, CO ₂etc.) level.

In operation, in the chamber of fuel air mixture in burner 12, burn, thereby form hot pressure exhaust.Burner 12 guides exhaust to pass through turbine 18 towards air exit 20.In the time that turbine 18 is passed through in exhaust, exhaust promotes turbo blade so that axle 22 rotates along turbine system 10 axis.As shown in the figure, axle 22 can be connected to each parts of turbine system 10, comprises compressor 24.Compressor 24 also can comprise the blade that is connected to axle 22.In the time that axle 22 rotates, the blade in compressor 24 also can rotate, thereby is compressed from air and the guide air of air intlet 26 and entered in multitube fuel nozzle and/or burner 12 by compressor 24.Axle 22 also can be connected to load 28, and for example, load can be vehicle or dead load, as the propeller on generator or aircraft in power plant.Load 28 can comprise can be by any appropriate device of the rotation output power supply of turbine system 10.

Fig. 2 is according to the cross section perspective side elevation view of the burner 12 of embodiment.As shown in Figure 2, axial direction or axis 40 extend in the longitudinal direction along the central axis 41 of burner 12, radial direction or axis 42 towards or extend (for example, vertical with axis 40) away from central axis 41, and circumferential direction 44 is extended around axial axis 40 and central axis 41.Burner 12 comprises downstream 46 and upstream extremity or head end 48.Downstream 46 is positioned near turbine 18 first order, and upstream extremity 48 is contrary with downstream 46 and be positioned at the place far away with turbine 18 first order.Burner 12 comprises multiple housings and wall, and they impale burner 12 and comprise compressed air and fuel.From upstream extremity 48, burner 12 comprises the end housing body 52 that is connected to end plate 54.As shown in the figure, end plate 54 can be simple end plate, and it has comprised single fuel nozzle hole 58.But in some embodiment, end plate 58 will not comprise fuel nozzle hole 58.End plate 54 can be connected to end housing body 52 in many ways, and described mode comprises securing member or welding.Contrary with end plate 54, end housing body 52 is connected to fuel nozzle shell 56.In order to be connected to fuel nozzle shell 56, end housing body 52 comprises flange 60, and described flange 60 makes end housing body 52 can be attached to fuel nozzle shell 56.For example, end housing body 52 can for example, be connected to fuel nozzle shell 56 with the securing member (, threaded securing member, as bolt) that extends through multiple holes in flange 60 and fuel nozzle shell 56.

In direction 40, continue, burner 12 comprises back casing 62.Back casing 62 has comprised the first flange 64 and the second flange 66.The first flange 64 makes back casing 62 can be connected to fuel nozzle shell 56.Exactly, the first flange 64 can comprise multiple holes 68, and described hole 68 allows securing member (for example, threaded securing member, as bolt) that back casing is connected to fuel nozzle shell 56.Contrary with the first flange 64, back casing is attached or contact fair water sleeves 70, and described fair water sleeves 70 helps the parts of cool burner 16.In radial direction 42, continuing is inwardly combustion liner 72.Combustion liner 72 comprises combustion reaction.Empty spatial placement, between fair water sleeves 70 and combustion liner 72, and can be called endless belt 74.Liner 72 extends around the axis 41 circumferential 44 of burner 12, and endless belt 74 extends around liner 72 circumferential 44, and fair water sleeves 72 extends around endless belt 74 circumferential 44.Endless belt 74 direct airflow are led to burner upstream extremity 48.More properly, in operation, enter the air chamber around fair water sleeves 70 from the air-flow 76 of compressor 24.Fair water sleeves 70 comprises radially injects hole 78, and the described hole 78 of radially injecting can and enter in endless belt 74 by fair water sleeves 70 compressed air stream 76.At air 76, by after hole 78, endless belt 74 guides compressed air 76 towards upstream extremity 48.In upstream extremity 48, compressed air 76 can turn to or redirect towards one or more fuel nozzle 80.Fuel nozzle 80 is configured for partly-premixed air and the fuel of closing, to form fuel air mixture 82.Fuel nozzle 80 is discharged into fuel air mixture 82 in combustion zone 84, in described combustion zone 84, combustion reaction occurs.Combustion reaction produces hot pressure combustion product 86.These combustion products 86 are advanced subsequently and are arrived turbine 18 by transition piece 88, thereby drive turbo blade to produce torque.

As above explanation, burner has comprised micro-mixer system 16.Micro-mixer system 16 comprises fuel nozzle shell 56, fuel nozzle 80, inlet flow rate adjuster 90 and rear board component 92.Following detailed description, micro-mixer system 16 functions are to protect multitube fuel nozzle 80 in case fragment and hot growth/gradient; And the each micro-mixer pipe in nozzle 80 is provided to air-flow and the fuel of suitable ratio, thereby reduce unexpected discharge.Micro-mixer system 16 can comprise multiple fuel nozzles 80, and described fuel nozzle 80 comprises multitube fuel nozzle and/or other fuel nozzles (for example, rotational flow guide vane nozzle).In illustrated embodiment, micro-mixer system 16 comprises multitube fuel nozzle 94 and the center fuel nozzle 96 on duty being supported by fuel nozzle shell 56.Fuel nozzle 80 is by fuel and air combination, thereby formation fuel air mixture is for burning in combustion zone 84.As multitube fuel nozzle 94, nozzle 96 on duty is by fuel and air combination, thereby formation is for the fuel air mixture of burning.But nozzle 96 on duty can contribute to the combustion flame of grappling for remaining fuel nozzle 94.

Fig. 3 is according to the side view of the micro-mixer system 16 of embodiment.As above explanation, micro-mixer system 16 comprises fuel nozzle shell 56, inlet flow rate adjuster 90 and rear board component 92.Fuel nozzle shell 56 radial support multitube fuel nozzle 80(, in fuel nozzle shell 56) and provide tie point for inlet flow rate adjuster 90 and rear board component 92.In addition, fuel nozzle shell 56 allows the radial fuel that is implemented to fuel nozzle 80 to carry (, in radial direction 42).Radial support and fuel are carried and are made burner 12 can use simple end plate 54 and increase useable surface area for multitube fuel nozzle 94.

Fuel nozzle shell 56 for example comprises first ring structure 120(, outer wall) and the second ring structure or mounting structure 122(are for example, outward flange).As above explanation, fuel nozzle shell 56 is connected to end housing body 52 and back casing 62.Exactly, the second ring structure 122 is connected to end housing body 52 and back casing 62, thus micro-mixer system 16 is fixed in burner 12.First ring structure 120 and the second ring structure 122 can be concentrically with respect to one another, and by multiple pole 124(for example, radial support arms or wing) link together.Pole 124 can be integrated into fuel nozzle shell 56.For example, first ring structure 120, the second ring structure 122 and pole 124 can be used and be added the processing of technique (additive process) cause blank, casting or growth.In other embodiment, first ring structure 120, the second ring structure 122 and pole 124 can connect by welding, brazing, bolt or other securing members.As shown in the figure, pole 124 can be shaped according to aerodynamics.For example, pole 124 can have wing shapes or other types aerodynamic shape.Aerodynamic shape makes pole 124 reduce air-flow wake flow can be between air-flow is by first ring structure 120 and the second ring structure 122 time.Wake flow reduces to be reduced vibration and enters the air-flow in inlet flow rate adjuster 90.Pole 124 also can allow the radial fuel that is implemented to fuel nozzle 94 to carry.Exactly, pole 124 can comprise the hole being communicated with the pore-fluid in the second ring structure 122 and first ring structure 124.Therefore, fuel can flow subsequently from being connected to the external source 125 of fuel flange 126, by fuel nozzle shell 56 and enter fuel nozzle 94, but not by end plate 54.Fuel nozzle shell 56 also can comprise cooling hole 128.Cooling hole 128 makes cooling blast can flow into (for example, in radial direction 42) in fuel nozzle shell 56, with cooling multitube fuel nozzle 94 and rear board component 92, to extend thus the operation lifetime of multitube fuel nozzle 94 and rear board component 92.

Fig. 4 is the decomposition perspective cross-sectional view of micro-mixer system 16.As shown in the figure, micro-mixer system 16 can be modular system, and it has promoted the attached of parts and has separated.Exactly, micro-mixer system 16 attached entrance flow regulator 90 and rear board component 92 it is separated from fuel nozzle shell 56 removedly.Ability attached and that separate inlet flow rate adjuster 90 and rear board component 92 makes easily to approach fuel nozzle 94 for safeguarding or changing.In addition, the modularity of increase can cause that assembling/unloading process is more simple, the maintenance process time is efficient, change the less and performance of operation increases.

As shown in the figure, inlet flow rate adjuster 90 extends around axis 41 circumferential 44, and can have the wall of ring-type substantially, and the wall of described cardinal principle ring-type has the external diameter 150 that is less than first ring structure 120 internal diameters 152.Difference on diameter can axial 40 slides in first ring structure 120 inlet flow rate adjuster 90.Inlet flow rate adjuster 90 subsequently can the attached or installation by the first installation portion 153.The first installation portion 153 can comprise the hole 158 in hole 156 and the inlet flow rate adjuster 90 in first ring structure 120, multiple securing member 154, first ring structure 120.Securing member 154 is connected to first ring structure 120 by the corresponding hole 158 in hole 156 and inlet flow rate adjuster 90 in first ring structure 120 by inlet flow rate adjuster 90.Securing member 154 can be bolt, rivet, pin or other removable securing members.Or inlet flow rate adjuster 90 can be by brazing, welding or or even welding/brazing and bolt or the incompatible first ring structure 120 that is connected to of stack of rivets.In other embodiment, the diameter 150 of inlet flow rate adjuster 90 can be greater than the diameter 152 of first ring structure 120, so that inlet flow rate adjuster 90 can axial 40 slipped over and be connected to first ring structure 120 outsides.

Rear board component 92 extends around axis 41 circumferential 44, and can have the wall of the cardinal principle ring-type that can be connected to fuel nozzle shell 56.Rear board component 92 can limit external diameter 160, and described external diameter 160 is less than the internal diameter 152 of first ring structure 120.Difference on diameter can axial 40 slides in first ring structure 120 rear board component 92.Rear board component 92 is attached or be installed to fuel nozzle shell 56 by the second installation portion 161.The second installation portion 161 can comprise the hole 166 in first ring structure 120, multiple securing member 162, hole 164 and rear board component 92.Securing member 162 is connected to first ring structure 120 by the corresponding hole 166 in hole 164 and rear board component 92 in first ring structure 120 by rear board component 92.Securing member 162 can be bolt, rivet, pin or other removable securing members.Or rear board component 92 can or be connected to first ring structure 120 by bolt or rivet welding/brazing at correct position by brazing, welding.In order to control cooling-air in order to avoid by between rear board component 92 and first ring structure 120, micro-mixer system 16 for example can comprise seal 168(between rear board component 92 and first ring structure 120, sealing hoop).In other embodiment, the diameter 160 of rear board component 92 can be greater than the diameter 152 of first ring structure 120, so that rear board component 92 can axial 40 slipped over and be connected to first ring structure 120 outsides.

Fig. 5 is the perspective front end view of fuel nozzle shell 56 embodiment, fuel nozzle 94(is shown for example, multitube fuel nozzle).Exactly, Fig. 5 is illustrated in the fuel nozzle container 190 of fuel nozzle shell 56 in the difference fuel nozzle 94 in assembling stage.For example, in illustrated embodiment, one in fuel nozzle 94 is arranged in fuel nozzle container 190 completely, and the second fuel nozzle 94 is just being prepared to be inserted in adjacent fuel nozzle container 190.For diagram object, residual fuel nozzle container 190 is empty (, the 3rd fuel nozzle 94 not being installed).In illustrated embodiment, each fuel nozzle container 190 has truncation cheese girth 188, and described truncation cheese girth 188 can be limited with relative convergence sidepiece 191 by relative bent side 189.In addition, shown in fuel nozzle shell 56 there is the fuel nozzle container 190 of three equal sizes, each have a truncation cheese girth 188.In other embodiment, fuel nozzle shell 56 can have 2,3,4,5,6,7,8,9,10 or the more fuel nozzle container 190 with truncation cheese girth 188.But each fuel nozzle container 190 can similar any shape, as circle, rectangle, triangle, cheese or any other appropriate geometry.

Shown in fuel nozzle 94 there is truncation cheese girth 91, described truncation cheese girth 91 can be limited with relative convergence sidepiece 95 by relative bent side 93.Truncation cheese girth 91 is set profile or is configured as the truncation cheese girth 188 for being coupled to container 190.Fuel nozzle 94 for example comprises multiple micro-mixer pipe 192(of being arranged in plate 194,196 and 198, mixing tube).In some embodiment, multitube fuel nozzle 94 can comprise 5 to 1000,10 to 500,20 to 250 or 30 to 100 pipes 192, and they are essentially parallel to each other along axis 41.Each pipe 192 can be approximately 0.25 to 5 centimetres, 0.5 to 3 centimetre or 1 to 2 centimetre on diameter.Plate 194,196 and 198 is axially offset to one another apart from 200 and 202, thereby forms the chamber with fuel nozzle shell 56.In the present embodiment, have three gripper shoes, but in other embodiment, may have two or more gripper shoes (for example, 2,3,4,5,6 etc.).In this way, plate 194,196 and 198 with given pattern support, interval and arrange micro-mixer pipe 192.In illustrated embodiment, pipe 192 comes out along the sidepiece 93 and 95 of each fuel nozzle 94.In other words, each fuel nozzle 94 does not comprise its oneself special shell, and on the contrary, fuel nozzle shell 56 is as the public or shared shell of multiple fuel nozzles 94.Therefore, each fuel nozzle 94 can be described as tube bank 192, and it can be axial 40 inserts corresponding container 190 in shells 56 and from wherein removing.

Fig. 6 is the front view of fuel nozzle shell 56, and described fuel nozzle shell 56 is configured for and for example supports multiple fuel nozzle 80(, multitube fuel nozzle 94, center fuel nozzle 96 etc.) and provide tie point for inlet flow rate adjuster 90 and rear board component 92.As above explanation, fuel nozzle shell 56 has comprised first ring structure 120 and the second ring structure 122.For fuel nozzle shell 56 is connected to adjacent burner shell, the second ring structure 122 comprises multiple holes 220.Hole 220 can receive the securing member (for example, threaded securing member or bolt) that makes fuel nozzle shell 56 can be connected to the flange on burner end housing body 52 and burner back casing 62.First ring structure 120 and the second ring structure 122 can be around axis 41 concentrically with respect to one another.As shown in the figure, first ring structure 120 limits external diameter 222, and described external diameter 222 is less than the internal diameter 224 of the second ring structure 122.Difference 226 on diameter forms the gas channel 228 between first ring structure 120 and the second ring structure 122.Gas channel 228 makes air can flow through in the upstream direction fuel nozzle shell 56, flows to end plate 54.

Gas channel 228 is separated by the pole 124 that first ring structure 120 is connected to the second ring structure 122.In illustrated embodiment, fuel nozzle shell 56 can comprise two kinds of poles: (1) fuel carries pole 230; And (2) do not carry the pole 232 of fuel.Pole 124 also can be integrated into fuel nozzle shell 56 and be configured for the resonance reducing in fuel nozzle shell 56.For example, pole 124 can be shaped according to aerodynamics, to reduce by the wake flow in the air-flow of gas channel 228.In addition, pole 124 can provide the hardness of appropriate amount, so that the resonant frequency of the vibration of detuning vibration frequency or change fuel nozzle shell 56.For example, in the present embodiment, fuel nozzle shell 56 comprises that three fuel poles 230 and three support pole or structural uprights 232.In other embodiment, fuel nozzle shell 56 for example can comprise more fuel pole 230(, 1,2,3,4,5,6,7,8,9,10 or more), or more branched support pole 232(is for example, and 1,2,3,4,5,6,7,8,9,10 or more).In other embodiment, some or all of pole 124 can be more greatly and/or are harder, so that tuned resonance or the specific location in fuel nozzle shell 56 provide other support.

As above explanation, fuel nozzle shell 56 allows the radial fuel 42 that is implemented to fuel nozzle 80 to carry.Fuel nozzle shell 56 receives fuel by the fuel flange 126 that is connected to the second ring structure 122 outer surfaces 234.When by fuel flange 126, fuel enters the hole 236 in the second ring structure 122.Passing through after hole 236, fuel enters fuel pole 230, and described fuel pole 230 comprises the hole 238 that leads to first ring structure 120 mesopores 240.When by the second ring structure 120, fuel enters fuel nozzle container 190, uses for fuel nozzle 80.As above explanation, the radial support of being undertaken by fuel nozzle shell 56 and fuel are carried end plate 54 can be simplified, and increase useable surface area (for example, the quantity of micro-mixer pipe 192 and/or size) for multitube fuel nozzle 94 in first ring structure 120.

In the present embodiment, there are three fuel nozzle containers 190 that separated by partition wall radially or plate 242.But, for example can there is any quantity fuel nozzle container 190(, 1,2,3,4,5,6 or more).As shown in the figure, on-fuel pole 232 is alignd with plate 242, and fuel pole 230 is positioned between wall 242 between two parties simultaneously.But in other embodiment, fuel pole 230 and on-fuel pole 232 can be positioned on other places.Partition wall radially or plate 242 are connected to first ring structure 120 and are for example connected to tricyclic structure 244(, the first inwall).Tricyclic structure 244 can be concentric and limit central container 246 with first ring structure 120 and the second ring structure 122.Central container 246 is configurable can contribute to grappling center fuel nozzle or the nozzle on duty 96 of the combustion reaction of multitube fuel nozzle 94 around for receiving.But in other embodiment, central container 246 is configurable for receiving circular multitube fuel nozzle.In addition, other embodiment can have more greatly, less or without central container 246.In illustrated embodiment, fuel nozzle container 190 has truncation cheese girth 188, and central container 246 is circular.But fuel nozzle container 190 and central container 246 can similar any shapes, as circle, rectangle, triangle, cheese or any other appropriate geometry.As above explanation, fuel nozzle shell 56(, first ring structure 120, tricyclic structure 244 and partition wall radially 242) shell for multitube fuel nozzle 94 is provided valuably.Therefore, each fuel nozzle 80 does not require its oneself stand-alone shell, and therefore can change with low cost more.

Fig. 7 is according to the front view of the fuel nozzle shell 56 of embodiment.As shown in the figure, fuel nozzle shell 56 is radially connected to six fuel flanges 126.Fuel nozzle shell 56 receives fuel and fuel radially 42 is transported to fuel nozzle container 190 from fuel flange 126, uses for fuel nozzle 80.As above explanation, entering before fuel nozzle container 190, fuel is by the hole in the second ring structure 122, fuel pole 230 and first ring structure 120.In illustrated embodiment, each fuel nozzle container 190 is by two fuel flange 126 feed.Two fuel flanges 126 are carried to first ring structure 120 by fuel from the second ring structure 122 by two corresponding fuel poles 230.In other embodiment, for example can there is additional fuel flange 126(for each fuel nozzle container, 1,2,3,4,5 or more fuel flange 126), they by respective amount fuel pole 230(for example, 1,2,3,4,5 or more fuel pole 230) transfer the fuel.

As Fig. 7 further as shown in, plate 242 radially can comprise the hole 248 that makes fuel can flow to from a fuel nozzle container 190 adjacent fuel nozzle container 190.For example, hole 248 can be distributed on whole plate 242, to help, fuel is more evenly distributed between the pipe 192 of fuel nozzle 94.In further example, the quantity of hole 248 (for example, 1 to 1000), size (for example, diameter), shape (for example, circle, ellipse, triangle, square, polygon etc.), axial 40 positions and radially 42 positions can be different, to control the distribution of fuel between container 190, and therefore control the distribution of fuel between multiple pipes 192 of fuel nozzle 94.In some embodiment, eachly in plate 242 can not comprise hole 248, for example comprise more concrete dynamic modulus 248(, 0,1,2,3,4,5,10,15,20,25 or more hole 248), or hole 248 quantity between plate 242 are not identical.For example, a plate 242 can comprise two holes 248, and remaining plate has respectively five and ten holes 248.Fuel in embodiment with hole 248 in plate 242, can there is fuel flange 126 and fuel pole 230 still less, because can flow freely between fuel nozzle container 190.Therefore, single fuel flange 126 and fuel pole 230 can be fed to fuel nozzle container 190 by all fuel.In addition, Fig. 7 illustrates that tricyclic structure 244 can comprise hole 250.Hole 250 allows the fuel in fuel nozzle container 190 to enter central container 246.In the present embodiment, there are three holes 250, but, in different embodiment, for example can there is varying number hole 250(, 0,1,2,3,4,5,10,15 or more hole 250).In other embodiment, tricyclic structure 244 can comprise the hole 250 being only communicated with some fuel nozzle containers 190.For example, tricyclic structure 244 can only comprise the hole 250 between central container 246 and one of them fuel nozzle container 190.

Fig. 8 is according to the front view of the fuel nozzle shell 56 of embodiment.In illustrated embodiment, fuel nozzle shell 56 comprises three fuel nozzle containers 190.Each region that occupies interior approximately 120 degree of first ring structure 120 in these fuel nozzle containers 190.Actual, Fig. 8 illustrates and without the embodiment of the central container shown in accompanying drawing before.Although Fig. 8 illustrates only three fuel nozzle containers 190, the fuel nozzle container 190(that other embodiment can comprise the varying number being separated by plate 242 for example, 1,2,3,4,5,6,7,8,9,10 or more fuel nozzle container 190).In addition, each the occupying in first ring structure in these fuel nozzle containers 190 equates or different region of measuring.For example, a fuel nozzle container 190 can occupy 180 degree of first ring structure 120, and residual fuel nozzle container 190 has occupied respectively 90 degree.

Fig. 9 is according to the partial cross section view of the micro-mixer system 16 of embodiment.As above explanation, micro-mixer system 16 comprises fuel nozzle shell 56, fuel nozzle 80, inlet flow rate adjuster 90 and rear board component 92.Fuel nozzle shell 56 is radial support micro-mixer system 16 in the following manner: be connected between end housing body 52 and back casing 62, or more properly, be connected to the flange 60 of end housing body 52 and the first flange 64 of back casing 62.In the time that fuel nozzle shell 56 is connected between end housing body 52 and back casing 62, fuel nozzle shell 56 can radial support fuel nozzle 80 and fuel is radially fed to fuel nozzle 80.The multitube fuel nozzle 94 that fuel nozzle 80 can be multitube fuel nozzle 94 or combines with fuel nozzle 96 on duty.In illustrated embodiment, fuel nozzle shell 56 supports multitube fuel nozzle 94 and center fuel nozzle 96 on duty.

In operation, fuel nozzle 80(for example, multitube fuel nozzle 94 and fuel nozzle on duty 96) by the combination of fuel and air, thereby form fuel air mixture for burning in combustion zone 84.Fuel nozzle 80 receives air-flow from compressor 24.As above explanation, compressor 24 is discharged into air-flow in the air chamber around burner 12 downstream 46.Radially injection hole 78 in fair water sleeves 70 makes air-flow 76 and to enter endless belt 74 by fair water sleeves 70.The endless belt 74 being formed by fair water sleeves 70 and combustion liner 72 is by the lead upstream extremity 48 of burner 16 of air-flow.In upstream extremity 48, air-flow 76 enters inlet flow rate adjuster 90.As described in more detail below, inlet flow rate adjuster 90 is configured for and helps circumferential 44 distribution air-flows around fuel nozzle 94, thereby helps the air-flow of more equal equivalent to be provided in each pipe 192 of fuel nozzle 94.In addition, inlet flow rate adjuster 90 can serve as filter, to help to stop particulate matter to lead among container 190, thereby helps to reduce the obstruction of pipe 192.After 90s by inlet flow rate adjuster, compressed air enters in the pipe 192 of multitube fuel nozzle 94.Pipe 192 combines compressed air and fuel 260, thereby is formed on the fuel air mixture 262 of burning in combustion zone 84.Fuel 260 radially enters fuel nozzle shell 56 by fuel flange 126.Fuel 260 passes the second ring structure 122, fuel pole 230 and first ring structure 120 by corresponding hole 236,238 and 240 subsequently.In the time that fuel 260 passes through first ring structure 120, fuel 260 enters fuel nozzle container 190, uses for fuel nozzle 94.As above explanation, the radial support of being undertaken by fuel nozzle shell 56 and fuel are carried end plate 54 can be simplified, and increase useable surface area (for example, the quantity of micro-mixer pipe 192 and/or size) for multitube fuel nozzle 94.

Multitube fuel nozzle 94 comprises multiple pipes 192 of the hole 264,266 and 268 extending through in respective plate 194,196 and 198.In illustrated embodiment, multitube fuel nozzle 94 comprises three plates 194,196 and 198, and they are axially offset to one another to define chamber 270 and 272.In the time that fuel 260 enters multitube fuel nozzle 94, first fuel 260 enter chamber 270.Fuel 260 was distributed in whole chamber 270 before flowing to downstream in chamber 272.Chamber 270 also contributes to pressure and the flow of balance around the fuel of all pipes 192.As shown in the figure, plate 196 comprises the hole 274 that allows fuel to leave chamber 270 and enter chamber 272.In some embodiment, pore gap 266 can form adequate space and flow to chamber 272 from chamber 270 around pipe 92 for fuel.In other embodiment, pore gap 266 and hole 274 can make fuel 260 to flow to chamber 272 from chamber 270.Hole 266 and/or 274 is configured for and helps fuel to be distributed to more equably among chamber 272, thus pressure and the flow of balance fuel further before entering pipe 192 subsequently.In chamber 272, fuel 260 by fuel inlet or groove 276(for example, 1 to 100 fuel inlet) enter pipe 192.In the time that fuel 260 passes through fuel inlet 276, fuel 260 mixes with the air 76 by air intake 278.By export 280 leave before, fuel air mixture 262 is advanced subsequently by managing 192.In illustrated embodiment, fuel inlet 276 is in chamber 272.But in other embodiment, fuel inlet 276 can be in chamber 270 or at chamber 270 and 272 in both.In other embodiment, fuel nozzle 94 can not comprise plate 196, and fuel inlet 276 can be between plate 194 and plate 198.

As above explanation, multitube fuel nozzle 94 can comprise plate 194,196 and 198.Plate 194,196 and 198 can be fixed or be removable with respect to other supporting constructions of pipe 192, fuel nozzle shell 56 and/or burner 16.For example, plate 194,196 can have being fixedly connected with of forming by welding, brazing, bolt and/or formation interference engagement with pipe 192 with 198.In further example, movably connector 282(for example, elastic metallic seal) can be positioned between the one or more and fuel nozzle shell 56 in plate 194,196 and 198.Movably connector 282 can move in response to pipe 192 thermal expansion and contraction one or more plates 194,196 and 198 on axial direction 40.In illustrated embodiment, plate 194,196 has and is fixedly connected with pipe 52 with 198, palette 194 and 198 and fuel nozzle shell 56 for example there is movably connector 282(, elastic metallic seal).In another embodiment, plate 194 can have and is fixedly connected with pipe 192 with fuel nozzle shell 56, and plate 196 and 198 and fuel nozzle shell 56 there is movably connector 282.In another embodiment, plate 198 can have and is fixedly connected with and for example has movably connector 282(with fuel nozzle shell 56 with pipe 192, elastic metallic seal), for example, and plate 194 has and is fixedly connected with and has movably connector (, slip joint) with pipe 192 with fuel nozzle shell 56 with 196.In another embodiment, plate 196 has and is fixedly connected with and (for example has movably connector with fuel nozzle shell 56 with pipe 192, elastic metallic seal), for example, and plate 194 has and is fixedly connected with and has movably connector (, slip joint) with pipe 192 with fuel nozzle shell 56 with 198.In other embodiment, plate 194,196 can have and is fixedly connected with and has movably connector (for example, elastic metallic seal) with fuel nozzle shell 56 with pipe 192 with each in 198.In each in these embodiment, movably connector 282(for example, elastic metallic seal) be configured in response to the thermal expansion of pipe 192, fuel nozzle shell 56 or burner 16 any other structures or thermal contraction and expand and shrink, thereby minimizing heat-induced stress maintains fluid tight seal simultaneously.

In system 10 operations, in multitube fuel nozzle 94, each pipe 192 is received approximate equivalent air-flow and is received fuel 260 by the fuel inlet 276 in chamber 272 by inlet flow rate adjuster 90.Fuel and air be in the interior mixing of each pipe 192, and export 280 discharges as fuel air mixture 262 by fuel air mixture subsequently, in the interior burning of burner 16.Should understand, near outlet 280, temperature raise because of the interior burning of burner 16.In addition, air-flow 284 temperature can essence be greater than the temperature of fuel flow 260.For example, air-flow 284 temperature can be approximately 250 to 500 degrees Celsius, and fuel flow 260 temperature can be approximately 20 to 250 degrees Celsius.For example, due to these thermogrades, part (, pipe 192, fuel nozzle shell 56 etc.) material composition and other factors, pipe 192 may be through expanded by heating in 16 operations of micro-mixer system.Movably connector 282(for example, elastic metallic seal) be configured for and absorb this thermal expansion (with any thermal contraction, for example, in shutdown process) so that each part of protection multitube fuel nozzle 94 and burner 16.Not movably connector 282(is not for example, elastic metallic seal) time, pipe 192, fuel nozzle shell 56 and other supporting constructions may be subject to significant thermal stress, and it can cause too early wearing and tearing, stress crack and the life-span of multitube fuel nozzle 94 to reduce.Therefore, movably connector 282(for example, elastic metallic seal) operability, performance and life-span (for example, the stress of minimizing and fatigue) that can help to improve multitube fuel nozzle 94.For example, movably connector 282 can make multitube fuel nozzle 94 can bear the larger temperature difference, thereby allows to strengthen the property in the situation that not damaging multitube fuel nozzle 94 or micro-mixer system 16.Discuss in detail further as follows, movably connector 282 maintains the working seal between fuel nozzle shell 56 and plate 194 and 198, also moves axially because managing 192 thermal expansion or shrinking to realize simultaneously.

Figure 10 is the sectional view that the system of micro-mixer shown in Fig. 9 16 10-10 along the line obtains, and elastic metallic seal 300(is shown for example, metal bellows 302) embodiment.Following discussion, metal bellows 302 comprises that it can expand and shrink on axial direction 304 with one or more turnings or the wall 303 that turns round.As shown in figure 10, elastic metallic seal 300(for example, metal bellows 302) between fuel nozzle shell 56 and plate 198, extend, thereby form the working seal between fuel nozzle shell 56 and plate 198.Plate 198 is fixed to pipe 192, and therefore, plate 198 moves in response to thermal expansion with pipe 192 together with shrinking, and elastic metallic seal 300(is for example, metal bellows 302) on axial direction 304, expand and shrink.In illustrated embodiment, elastic metallic seal 300 is arranged between fuel nozzle shell 56 and plate 198, is for example positioned at bag 306(, ring-type bag or fan-shaped bag) in, described bag 306 can be by groove 308(relative with plate 198 peripheries 310 in fuel nozzle shell 56 for example, annular recess or scalloped recess) form.Groove 308 for example can be arranged on the inner surface 312 of the second ring structure 120 and the inner process of fuel nozzle shell 56 or lip 314(, annular lip or fan-shaped lip) between.Bag 306(for example, is formed by groove 308 and part 310,312 and 314) substantially extend along interface between fuel nozzle shell 56 and plate 198, thus the working seal that can expand and shrink on axial direction 304 is provided.

In some embodiment, elastic metallic seal 300(for example, metal bellows 302) fuel nozzle shell 56 and/or plate 198 is fixing or fixing (, moving freely) relatively.For example, seal 300 can have relative first end 316 and the second end 318, and described first end 316 and the second end 318 can welding, brazing, bolts or be otherwise fixed to groove 308 and periphery 310.But one or two in end 316 and 318 can not be fixed to fuel nozzle shell 56 or plate 198.In addition, elastic metallic seal 300(for example, metal bellows 302) can in wall 303, have one or more flexibilities turning, turn round, bending, folding or axially adjustable turning 320 substantially, 320 make seal 300 on axial direction 304, expand and to shrink thereby turn.In illustrated embodiment, elastic metallic seal 300(for example, metal bellows 302) there are multiple turnings that replace 320, it defines waveform patterns 322.For example, shown in seal 300 reverse direction five times, thereby in wall 303, limit five axially adjustable turnings 320.In addition, end 316 and 318 can be directed in radial direction 42.In the time that end 316 and 318 is directed in radial direction 42, elastic metallic seal 300 can promote the sealing between plate 198 and fuel nozzle shell 56.Exactly, if the pressure of fuel exceedes the air pressure of wall 198 opposition sides in chamber 270, metal bellows 302 can expand on axial direction 40 so, maintains thus sealing.But, if end 316 and 318 orientations are in the opposite direction, so metal bellows 302 can be in chamber 270 pressure of fuel be greater than on plate 198 opposition sides and shrink air pressure, thereby reduce the sealing force of metal seal 300.For this reason, end 316 can be according to different variation of fluid pressure on the opposition side of plate 194,196,198 with 318 orientation.For example, the metal seal 300 that is connected to plate 194 and 196 can be with the metal bellows 302 of the end 316 and 318 of opposite orientation shown in Figure 10.This can increase the ability of the metal seal 300 contacting with 196 with plate 194, to maintain in the time that plate 194 is different with fluid pressure on 196 opposition side and the sealing of shell 56.In other embodiment, seal 300 can comprise single axially adjustable turning 320, or the axially adjustable turning 320(of any quantity for example, 1 to 100 turning).Therefore, the turning 320 of seal 300 can limit the oscillation picture of C shape, U-shaped, V-arrangement, W shape, E shape or any type.In other embodiment, seal 300 can have O shape or J-shaped.In elastic metallic seal 300, the turning 320 of larger quantity can increase by 304 scopes that move axially.Elastic metallic seal 300 can be made up of any suitable metal of applying for high-temperature metal, described metal be for example stainless grade of steel 321, stainless grade of steel 347, stainless steel A-286, nickel alloy, cobalt alloy and nickel chromium triangle base superalloy (for example, or its any combination X-750).

Figure 11 be have be suitable for Fig. 4 to 6 multitube fuel nozzle 94 fan-shaped configuration 340(for example, truncation cheese) the front end view of elastic metallic seal 300 embodiment.As shown in the figure, fan-shaped configuration 340 comprises having two substantially parallel side portions 342 and 344 and wedge shape or the truncation cheese of two non-parallel sidepieces 346 and 348.Sidepiece 342 and 344 is arcs, and sidepiece 346 and 348 is linear (for example, dispersing in radial direction 350).For example, but in some embodiment, the fan-shaped configuration 340 of seal 300 can comprise other shapes,, has the cheese of three sidepieces.In addition, some embodiment of seal 300 can be configured as circle, rectangle, triangle or other geometries.In the embodiment of Fig. 8, multitube fuel nozzle 94 becomes three around center fuel nozzle 12 fan-shaped with associated seal 300 sectionals.But it is fan-shaped that outer multitube fuel nozzle 94 and associated seal 300 can be divided into any quantity, for example, 1,2,3,4,5,6,7,8,9,10 or more fan-shaped.

Figure 12,13 and 14 is partial cross-sectional side view of the fuel nozzle of multitube shown in Fig. 9 94, is illustrated in wall 303, to have varying number axial adjustable and for example turn 320 elastic metallic seal 300(, metal bellows 302) embodiment.For example, Figure 12 is the partial cross-sectional side view of fuel nozzle 12 shown in Fig. 9, illustrates and has single turning or for example turn round 320(, U-shaped or C shape 352) the embodiment of elastic metallic seal 300.Figure 13 is the partial cross-sectional side view of the fuel nozzle of multitube shown in Fig. 9 94, illustrates and has multiple turnings of waveform patterns of limiting 322 or for example turn round 320(, E shape or W shape 354) the embodiment of elastic metallic seal 300.Figure 14 is the partial cross-sectional side view of the fuel nozzle of multitube shown in Fig. 9 94, illustrates and has the embodiment limiting than multiple turnings of the larger waveform patterns 322 of Figure 10 or 320 the elastic metallic seal 300 of turning round.Specifically, the waveform patterns 322 of Figure 14 has 9 turns or turns round 320, and it can be described as waveform, vibration or zigzag pattern 356.In other embodiment, pattern 356 can have any amount of turning or turn round 320.For example, in the application with the larger temperature difference, for example turn 320 elastic metallic seal 300(, metal bellows 302 with a large amount of) can be used for allowing to move axially more greatly, still keep the working seal between fuel nozzle shell 56 and the plate 198 of multitube fuel nozzle 94 simultaneously.In addition, in Figure 12, each embodiment of 13 and 14, opposite ends 316 can relative fuel nozzle shell 56 with 318 and plate 198 is fixing or fixing (, can move).For example, can fix for one in end 316 and 318, and another end is unfixed, thereby simplifies the installation of fuel nozzle 12 and remove.

Figure 15 is the decomposition diagram of rear board component 92.Rear board component 92 shields multitube fuel nozzle 94 in order to avoid the combustion reaction of fuel air mixture 262 and cooling multitube fuel nozzle 94 in combustion zone 84 make rear board component 92 help to extend the operation lifetime of multitube fuel nozzles 94.Rear board component 92 for example comprises rear plate 370, shock plate 372, the first cylinder 374(, outer wall), the second cylinder 376(for example, inwall) and the first sealing hoop 378(is for example, lip ring (hula seal)) and the second sealing hoop 380(is for example, lip ring).Sealing hoop 378 and 380 is seals of cardinal principle ring-type, has the wall 377 of ring-type, and the wall 377 of described ring-type first increases and reduces afterwards to limit arc-shaped cross-section or spring element 379 on diameter.Arc-shaped cross-section 379 helps, in accommodate thermal expansion and contraction in the radial direction, to maintain sealing simultaneously.As shown in the figure, rear plate 370 and shock plate 372 comprise respective tube hole 382 and 384, and they can realize attached on the pipe 192 of multitube fuel nozzle 94 of rear board component 92.Rear plate 370 and shock plate 372 also can comprise respective center nozzle hole or passage 386 and 388.Central nozzle hole 386 and 388 makes the second cylinder 376 can extend through shock plate 372 and rear plate 370 and by central passage 385 receiving center fuel nozzles or nozzle on duty 96.Rear board component 92 use pin 162(are referring to Fig. 9) be attached to fuel nozzle shell 56, pin 162 is for example connected to the first cylinder 374(by hole 390, radially installs).Pin 162 makes rear board component 92 radial growths, rotates or moves but can stop towards burner 12 rear ends.In addition, lock configuration makes other parts of rear plate 370 or rear board component 92 be easy to change.

In illustrated embodiment, for example, all mixing tubes 192 for fuel nozzle 94 in multiple containers of each reception fuel nozzle shell 56 in plate 370 and 372 (, three fan-shaped and/or truncation cheese layouts).In other words, not provide a separate board to each container 190, but illustrated embodiment is shared plate 370 and 372 between all containers 190, thereby limit integrated plate 370 and integrated plate 372.Integrated rear plate 370 has pore gap 382, described pore gap 382 be arranged on whole plate 370 substantially by fan-shaped spacing body 381(for example, radial separations space) for example, in fan-shaped (, cheese is fan-shaped) that separate, partition wall 242 general alignment between described fan-shaped spacing body 381 and container 190.Similarly, integrated shock plate 372 has pore gap 384, and described pore gap 384 is arranged on the whole plate 372 of cardinal principle, except fan-shaped spacing body 383, and partition wall 242 general alignment between described fan-shaped spacing body 383 and container 190.Therefore, the integrated structure of rear plate 370 and shock plate 372 can contribute to, for mixing tube 192 increases pore gap 382 coverages, also to have reduced potential leakage paths quantity simultaneously.Integrated plate 370 and 372 has also been simplified structure, installation, movement and the maintenance of micro-mixer system 16, has especially simplified and has managed 192 installation and remove.

Figure 16 is according to the sectional view of 16 16-16 along the line of micro-mixer system in Fig. 9 of embodiment.As shown in the figure, rear board component 92 is assembled into that rear plate 370 is connected to shock plate 372 and shock plate 372 is connected to the first cylinder 374.Rear plate 370, shock plate 372 and the first cylinder 374 can for example, connect by welding, brazing or securing member (, threaded securing member).Once assembling, rear board component 92 is connected to fuel nozzle shell 56 by the pin 162 that extends through the hole 390 in hole 164 and the first cylinder 374 in fuel nozzle shell 56.Air-flow is limited between rear board component 92 and combustion liner 72 by sealing hoop 378.As mentioned above, rear board component 92 allows to realize cooling and can stop the burning of fuel air mixture 262 in combustion zone 84 directly to contact with the pipe 192 in multitube fuel nozzle 94.Therefore, rear plate 370 can be made up of the material that can bear for a long time high temperature (for example, Hastelloy (hastalloy) X, Hai Na (haynes) 188, cochrome (cobalt chromium), Inco nickel (inconnel) etc.).In addition, rear plate 370 can comprise as the coating of thermal barrier coating (TBC) 400, to other heat protection is provided, thus the thermal wear on plate 370 be restricted to the heat transmission of pipeline 192 after reducing.

Rear board component 92 also can be combined to form air cooling chamber 402 with plate 198.As above explanation, fuel nozzle shell 56 comprises the cooling hole 128 of radial air, it can advance compressed air 76 and enters air cooling chamber 402 by annulus 74.In the time that air-flow 76 enters chamber 402, air-flow 76 is around pipe 192 eddy flows and it is carried out to convection current cooling (, heat being transferred away from managing 192).In addition, air-flow 76 can help to remove any fuel 260 in the air cooling chamber 402 that may be leaked between pipe 192 and wall 198, thereby essence reduces or elimination is accumulated in the fuel after rear plate 370.Chamber 402 guides cooling blast 76 towards shock plate 372 in direction 404.As shown in the figure, shock plate 372 is offset to form space 406 with rear plate 370.Space 406 forms pressure drop to attract air-flow 76 by impacting hole 408.In the time that air-flow 76 passes through shock plate 372, air-flow 76 impacts on the front end sidepiece 410 of rear plate 370, to impact cooling to plate 370.Impacting cooling after the front end sidepiece 410 of shock plate 370, air-flow 76 can be by spreading cooling hole and/or leaving between rear plate 370 and pipe 192.In the time that cooling-air 76 leaves rear board component 92, air-flow 76 in combustion zone 84, is protected micro-mixer system 16 in order to avoid thermal wear by heat and possible delivery of fuel thus.

In other embodiment, rear board component 92 can not comprise shock plate 372.Therefore, cooling blast 76 can directly contact the front end sidepiece 410 of rear plate 370, and subsequently by manage 192 and rear plate 370 between gap and/or leave by spreading cooling hole.Even if carry out coolingly, it is hotter than the miscellaneous part in micro-mixer system 16 that rear plate 370 also may become.But, make the rear board component 92 can radial growth to the pin of fuel nozzle shell 56 attached, rotate and downstream axial moves but stop.Therefore, micro-mixer system 16 reduces or has stoped mechanical load and the stress between rear board component 92 and fuel nozzle shell 56.

Figure 17 is the sectional view that comprises the rear plate 370 of pore gap 382 and the cooling hole 420 of diffusion.As above explanation, after cooling-air 76 impacts on the front end sidepiece 410 of plate 370 after, cooling blast 76 can be by spreading cooling hole 420 and/or leaving by pore gap 382.As shown in the figure, pore gap 382 has width 422 and pipe 192 has width 424.Difference 426 between width 422 and 424 forms annulus 428, leaves micro-mixer system 16 for cooling blast 76 by rear plate 370.Cooling blast 76 also can leave by spreading cooling hole 420.Spreading cooling hole 420 can be between some or all of pore gap 382.In some embodiment, can there is one between each in adjacent tubes hole 382 and for example spread above cooling hole 420(, 1,2,3,4,5 or more).Spreading cooling hole 420 can be perpendicular to plane 432 shapes of rear plate 370 or relatively rear plate 370 at an angle.For example, spread the angle 430 and 431 of cooling hole can opposite planar 432 be approximately 30 to 150 degree, 50 to 130 degree, 70 to 110 degree, 80 to 100 degree, 30 degree, 45 degree, 60 degree, 75 degree or 90 degree.In operation, spreading cooling hole 420 makes cooling blast film can cover the rear end 434 of rear plate 370.Cooling-air film can help to protect rear plate 370 to avoid the combustion reaction in burner 12.Although Figure 17 illustrates rear plate 370, identical air-circulation features can be applicable to shock plate 372.Exactly, the impact hole 408 of shock plate 372 relatively shock plate 372 planar shaped at an angle.Shock plate 372 for example also can comprise multiple impact hole 408(between pore gap 384,1,2,3,4,5 or more impact hole), with cooling rear plate 370 more effectively.

Figure 18 is the rear view of inlet flow rate adjuster 90.As above explanation, inlet flow rate adjuster 90 serves as filter, prevents that fragment from entering multitube fuel nozzle 94, and air-flow can be similar to be evenly distributed to the each pipe 192 in multitube fuel nozzle 94.Inlet flow rate adjuster 90 for example comprises the first cylinder 450(, outer wall), the second cylinder 452(for example, inwall) and the first cylinder 450 is connected to the plate 454 of the second cylinder 452.As shown in the figure, the first cylinder 450 comprises hole 158, and it makes inlet flow rate adjuster 90 can be connected to fuel nozzle shell 56.In addition, the first cylinder 450 for example also can comprise air-flow hole 456(, radially hole), described air-flow hole 456 each other vertically 40 and circumferential 44 spaced apart along the first cylinder 450.The diameter that hole 456 has can be less than the diameter of the pipe 192 in multitube fuel nozzle 94.Difference on diameter makes inlet flow rate adjuster 90 stop fragment in compressed air 76 by inlet flow rate adjuster 90 and enter pipe 192.In the present embodiment, air-flow hole 456 is positioned near plate 454.But, in other embodiment, air-flow hole 456 can be positioned on the first cylinder 450 with plate 454 opposition sides on, or air-flow hole 456 can be positioned on the first cylinder 450 circumference any point around.In illustrated embodiment, air-flow hole 456 is circular; But in other embodiment, hole can be rectangle, square or oval-shaped.In addition, hole 456 can be arranged to different pattern (for example, embarking on journey) around the first cylinder 450.

Plate 454 for example also can comprise multiple air-flow hole 458(, axial porosity).Similar hole 456, the diameter that hole 458 has can be less than the diameter of the pipe 192 in multitube fuel nozzle 94.Difference on diameter makes inlet flow rate adjuster 90 stop fragment in compressed air 76 by inlet flow rate adjuster 90 and enter pipe 192.As mentioned above, micro-mixer system 16 radially 42 is transported to multitube fuel nozzle 94 by fuel.Therefore, the region of plate 454 can be full of air-flow hole 458 substantially, reduces thus the pressure loss at compressed air 76 during by inlet flow rate adjuster 90.Similar air-flow hole 456, air-flow hole 458 can be circle, rectangle, square or oval-shaped.In addition, air-flow hole 458 can be arranged to pattern (for example, becoming the row of circular concentric) around the second cylinder 452.But in different embodiment, air-flow hole 458 can differently be arranged.The second cylinder 452 is placed in plate 454 and the center of restriction fuel nozzle hole 460.Center fuel nozzle hole 460 makes center fuel nozzle or fuel nozzle on duty 96 and to enter fuel nozzle shell 56 by inlet flow rate adjuster 90.In other embodiment, inlet flow rate adjuster 90 can not comprise center fuel nozzle hole 460, but alternately comprises additional air flow hole 458, and compressed air 76 is delivered to multitube fuel nozzle 94 by described additional air flow hole 458.

Figure 19 is the front perspective view of the adjuster of inlet flow rate shown in Figure 18 90.As shown in the figure, inlet flow rate adjuster 90 for example comprises partition wall or gripper shoe 470(, radial struts).Gripper shoe 470 is connected to the first cylinder 450, the second cylinder 452, plate 454, and is connected to and for example turns to guiding element 472(, turns to stator, baffle plate or wall).Gripper shoe 470 can for example, connect by welding, brazing or securing member (, threaded securing member), with to turning to guiding element 472 and the second cylinder 452 that other support is provided.Except providing support, gripper shoe 470 can help to be directed to special container 190 and multitube fuel nozzle 94 by the air-flow of header board 454 mesopores 458.In the present embodiment, inlet flow rate adjuster 90 comprises three gripper shoes 470 corresponding with three multitube fuel nozzles 94 in fuel nozzle shell 56.But, in other embodiment, for example can there is additional support plate 470(, 1,2,3,4,5,6,7,8,9,10 or more), it can be corresponding with the quantity of container 190 and multitube fuel nozzle 94.In addition, gripper shoe 470 can slave plate 454 extends to the end opposite 474 of the first cylinder 450, thus, between multitube fuel nozzle 94, divides by the air-flow of inlet flow rate adjuster 90.

Being similar to inlet flow rate adjuster 90 shown in the plate 370 of rear board component 92 and 372, Figure 18 and 19 can integrated (for example, single-piece) structure, and it shares between multiple containers 190, multiple fuel nozzle 94 and all pipe 192.In other words, hole 458 can essence cover whole plate 454, except and container 190 between the gripper shoe 470 of partition wall 242 general alignment.Therefore, hole 458 can help towards mixing tube 192, air-flow essence to be fed on whole plate 458 equably on axial direction 40, and hole 456 helps towards mixing tube 192, air-flow essence to be supplied around the first cylinder 450 equably in radial direction 42.Equally, hole 456 and 458 contributes to air-flow to be distributed to more equably all pipes 192, so that each pipe 192 receives the air stream of essence equivalent.In addition, the integrated structure of inlet flow rate adjuster 90 simplified fuel nozzle 94 and mixing tube 192 structure, install, remove and keep in repair.

As mentioned above, inlet flow rate adjuster 90 comprises and turns to guiding element 472.Turn to guiding element 472 can help air-flow to be directed to the outermost radial outside pipe 192 in multitube fuel nozzle 94.Exactly, turn to air-flow hole 456 direct airflow that guiding element 472 can be from the first cylinder 450.In other embodiment, turn to guiding element 472 air-flow can be directed to the outermost radial outside pipe 192 of multitube fuel nozzle 94 from hole 456 and 458, make thus air-flow essence to be distributed to equably the each pipe 192 in multitube fuel nozzle 94.

Figure 20 is the sectional view of inlet flow rate adjuster 90.As shown in the figure, turn to guiding element 472 to redirect the air-flow that enters inlet flow rate adjuster 90 by hole 456.Exactly, in the time that air-flow 76 enters inlet flow rate adjuster 90 by hole 456, air-flow contact turns to guiding element 472.Turn to guiding element 472 that air-flow 76 is turned to and direct airflow 76 flows along the inner surface 476 of inlet flow rate adjuster 90.In the time that air-flow is advanced near inner surface 476, inlet flow rate adjuster 90 makes outermost radial outside pipe 192 can receive with the radially inside tube 192 of multitube fuel nozzle 94 air-flow of roughly the same amount.In the present embodiment, turn to guiding element 472 that the air-flow that enters inlet flow rate adjuster 90 by hole 456 is turned to.But, in other embodiment, turn to guiding element 472 also can make the air-flow that enters inlet flow rate adjuster 90 by some holes 458 in plate 454 turn to.

Figure 21 is the sectional view of the embodiment of inlet flow rate adjuster 90.In illustrated embodiment, inlet flow rate adjuster 90 air-flow is not directed to multitube fuel nozzle 94 outermost radial outside pipe 192 turn to guiding element.On the contrary, air-flow hole 456 and the first cylinder 450 angulations 480,482 and 484, wherein angle 480,482 and 484 general orientation are on the downstream direction towards pipe 192.Hole 456 angles redirect the air-flow that enters inlet flow rate adjuster 90.More properly, hole 456 angles are impelled inner surface 476 Flow Structure Nearbies of air-flow at inlet flow rate adjuster 90, thus, the air-flow of the approximate equivalent receiving with radially inside tube 192 are fed on outermost radial outside pipe 192.Angle 480,482 and 484 can be approximately 90 to 170 degree, 110 to 150 degree or 130 to 140 degree, or is greater than approximately 100 degree, 120 degree, 140 degree or 160 degree.In some embodiment, hole 456 can have different angles, impels thus by the air-flow of different aperture 456 more approaching or mobile further from inner surface 476.For example, each in angle 480,482 and 484 can be different, or some in angle 480,482 and 484 can be equal to each other.In another embodiment, angle 480,482 and 484 can increase gradually to another from a hole 456 on axial direction 40.In other embodiment, angle 480,482 and 484 can reduce gradually to another from a hole 456 on axial direction 40.In each in these embodiments, hole 456 angles can contribute to approximate equivalent air-flow to be provided to the each pipe 192 in multitube fuel nozzle 94.

Figure 22 is the sectional view of the embodiment of inlet flow rate adjuster 90.Be similar to the embodiment in Figure 22, the adjuster of inlet flow rate shown in Figure 22 90 does not comprise and turns to guiding element.On the contrary, inlet flow rate adjuster 90 comprises hole 456 and 458, and they and the first cylinder 450 and plate 454 form respective angles.Exactly, hole 456 and the first cylinder 450 angulations 480,482 and 484, hole 458 is angulation 490,492,494 and 496.In the present embodiment, two angles that have in hole 456 are greater than 90 degree, and relative the first cylinder 450 of the 3rd hole is 90 degree.In addition, some holes 458 form with plate 454 angle (for example, angle 490 and 492) that is greater than 90 degree, and residual pore 458 forms 90 degree angles 494 and 496.Two holes 458 with non-perpendicular angle 490 and 492 increase with the combination (all angles are to be all greater than 90 degree, 100 degree, 110 degree, 120 degree, 130 degree, 140 degree, 150 degree, 160 degree or 170 degree) of the hole 456 that forms non-perpendicular angle 482 and 484 air-flow that arrives the outermost radial outside pipe 192 of multitube fuel nozzle 94 along the inner surface 476 of the first cylinder 450.Therefore, the hole 456 in the first cylinder 450 and the hole 458 along plate 454 rise to the air-flow of the outermost radial outside pipe 192 that reaches multitube fuel nozzle 94, make thus approximate equivalent air-flow enter the pipe 192 of multitube fuel nozzle 94.Angle 480,482,484,490,492,494 and 496 can be approximately 90 to 170 degree, 110 to 150 degree, 130 to 140 degree, or approximately 90 degree, 100 degree, 110 degree, 120 degree, 130 degree, 140 degree, 150 degree, 160 degree or 170 degree.In some embodiment, hole 456 and 458 can have different angles, guides thus by the air-flow of different aperture 456 and 458 more approaching or mobile further from inner surface 472.For example, each in angle 480,482,484,490,492,494 and 496 can be different, or some in can relative angle 480,482,484,490,492,494 and 496 are different.In another embodiment, angle 480,482 and 484 can increase gradually to another from a hole on axial direction 40.In another embodiment, angle 480,482 and 484 can reduce gradually to another from a hole on axial direction 40.The angle of angle 490,492,494 and 496 also can increase gradually to another from a hole in radial direction 42, or reduces gradually to another from a hole in radial direction 42.In addition, only some in hole 456 and 458 can form the angle that is greater than 90 degree, and residual pore forms the angle of 90 degree with the first cylinder 450 and the second cylinder 454.In the time that each pipe 192 receives approximate equivalent air-flow by flow regulator 90, multitube fuel nozzle 94 mixes and distribution fuel air mixture with suitable ratio, to realize best combustion, discharge, fuel consumption and power stage.Exactly, micro-mixer system 16 can reduce unexpected emission (for example, the NO from combustion gas turbine systems _x, CO, CO ₂etc.) level.

Technique effect of the present invention comprises a kind of modular micro-mixer system.Modular micro-mixer system promotes inspection, maintenance and the replacing to separate part, and described parts comprise multitube fuel nozzle, inlet flow rate adjuster, rear board component and elastic metallic seal (for example, metal bellows).As above explanation, fuel nozzle shell supports separate part, fuel is radially provided to multitube fuel nozzle simultaneously.Radial fuel is carried to make on burner, to use and is simplified end plate, and increases the spendable free space of pipe of multitube fuel nozzle.Other technologies effect comprises entrance flow regulator, and it can filter fragment and approximate equivalent air-flow is entered in the each pipe in multitube fuel nozzle from compressed air.In addition, micro-mixer system comprises rear board component, and described rear board component is configured for the cooling-air chamber that formation can the cooling multitube fuel nozzle of convection current, also can prevent that multitube fuel nozzle from contacting with the direct of combustion reaction in combustion zone.Finally, the wearing and tearing that elastic metallic seal reduces or stops the thermograde in multitube fuel nozzle to cause.Exactly, elastic metallic seal (for example, metal bellows) can expand in the axial direction or shrink, to reduce thermal expansion or the blockage effect of pipe, maintains the continuous operation sealing between fuel nozzle shell and multitube fuel nozzle simultaneously.

This description use-case discloses the present invention, comprises optimal mode, also makes any technical staff in affiliated field can both put into practice the present invention, comprise any method of manufacturing and using any device or system and execution to contain simultaneously.Scope of patent protection of the present invention is defined by claims, and can comprise other examples that one of skill in the art find out.If the structural element that these type of other examples have is identical with the letter of claims, if or the equivalent structure element that comprises of these type of other examples and the letter of claims there is no essential difference, these type of other examples are also in the scope of claims so.

Claims

1. a system, described system comprises:

Multiple multitube fuel nozzles, each multitube fuel nozzle has the multiple pipes that extend in the axial direction, and the each pipe in wherein said multiple pipes comprises air intake, fuel inlet and fuel air mixture outlet; And

Fuel nozzle shell, described fuel nozzle shell comprises:

Outer wall, described outer wall circumferentially extends around central axis;

Multiple radial walls, described multiple radial walls inwardly extend towards described central axis from described outer wall;

Multiple fuel nozzle containers, described multiple fuel nozzle containers are arranged in described outer wall, and wherein said multiple radial walls are separated from each other described multiple fuel nozzle container, and described multiple multitube fuel nozzle is arranged in described multiple fuel nozzle container;

Mounting structure, described mounting structure comprises from the outward extending multiple radial support arms of described outer wall.

2. the system as claimed in claim 1, the each fuel nozzle in wherein said multiple multitube fuel nozzles has the described multiple pipes that expose around respective fuel injector girth, and described fuel nozzle shell extends around the described girth of each fuel nozzle.

3. the system as claimed in claim 1, wherein said multiple fuel nozzle container comprises the first container and second container, and described multiple multitube fuel nozzle comprises the first multitube fuel nozzle being arranged in described the first container and is arranged on the second multitube fuel nozzle in described second container.

4. system as claimed in claim 3, wherein said multiple fuel nozzle containers comprise the 3rd container, and described multiple multitube fuel nozzle comprises the 3rd multitube fuel nozzle being arranged in described the 3rd container.

5. system as claimed in claim 4, wherein said the first container comprises the first cheese girth being limited at least partly by the first and second radial walls in described outer wall and described multiple radial wall, described second container comprises the second cheese girth being limited at least partly by second in described outer wall and described multiple radial wall and the 3rd radial wall, and described the 3rd container comprises the 3rd cheese girth being limited at least partly by first in described outer wall and described multiple radial wall and the 3rd radial wall.

6. system as claimed in claim 5, wherein said outer wall comprises the ring-type outer wall around border circular areas, wherein said first, second and the 3rd cheese girth comprise separately and account for the fan-shaped of described border circular areas approximately 120 degree.

7. the system as claimed in claim 1, wherein said fuel nozzle shell comprises the inwall coaxial with described outer wall cardinal principle, wherein said inwall is connected to described multiple radial wall.

8. system as claimed in claim 7, it comprises center fuel nozzle, described center fuel nozzle is arranged in the central passage that extends through described inwall.

9. the system as claimed in claim 1, the each container in wherein said multiple fuel nozzle containers is connected to a fuel channel by least one arm in described multiple radial support arms.

10. the system as claimed in claim 1, the each wall in wherein said multiple radial walls comprises at least one hole, between the adjacent container of described at least one hole in described multiple fuel nozzle containers, extends.